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Accession Number
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N20120012531
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Title
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Mission Life Thermal Analysis and Environment Correlation for the Lunar Reconnaissance Orbiter.
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Publication Date
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Jul 2012
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Media Count
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9p
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Personal Author
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H. Peabody M. B. Garrison
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Abstract
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Standard thermal analysis practices include stacking worst-case conditions including environmental heat loads, thermo-optical properties and orbital beta angles. This results in the design being driven by a few bounding thermal cases, although those cases may only represent a very small portion of the actual mission life. The NASA Goddard Space Flight Center Thermal Branch developed a procedure to predict the flight temperatures over the entire mission life, assuming a known beta angle progression, variation in the thermal environment, and a degradation rate in the coatings. This was applied to the Global Precipitation Measurement core spacecraft. In order to assess the validity of this process, this work applies the similar process to the Lunar Reconnaissance Orbiter. A flight-correlated thermal model was exercised to give predictions of the thermal performance over the mission life. These results were then compared against flight data from the first two years of the spacecraft's use. This is used to validate the process and to suggest possible improvements for future analyses.
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Keywords
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Correlation
Loads(Forces)
Lunar orbiter
Optical properties
Procedures
Reconnaissance
Spacecraft
Temperature effects
Thermal analysis
Thermal environments
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Source Agency
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National Aeronautics and Space Administration
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NTIS Subject Category
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46B - Fluid Mechanics
84 - Space Technology
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Corporate Author
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Goddard Space Flight Center, Greenbelt, MD.
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Document Type
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Conference proceedings
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Title Note
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N/A
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NTIS Issue Number
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1303
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Contract Number
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N/A
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